CN102390522B - Flow guide blade grid for short-distance takeoff and landing of airplane - Google Patents
Flow guide blade grid for short-distance takeoff and landing of airplane Download PDFInfo
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- CN102390522B CN102390522B CN201110284902.9A CN201110284902A CN102390522B CN 102390522 B CN102390522 B CN 102390522B CN 201110284902 A CN201110284902 A CN 201110284902A CN 102390522 B CN102390522 B CN 102390522B
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Abstract
The invention relates to a flow guide blade grid for short-distance takeoff and landing of an airplane. The chord lengths of an upper row wing, a middle row wing and a lower row wing are 10 percent of the chord length of a wing, the extension length of each row wing is 80 percent of the extension length of the wing, each row wing respectively deflects around the center line of the self length direction, the distances from the axial lines of the upper row wing, the middle row wing and the lower row wing to the front edge of the main wing in the chord direction are respectively 1.05, 1.15 and 1.25 times of the chord length of the main wing, the distances from the axial lines of the upper row wing, the middle row wing and the lower row wing to the front edge of the main wing in a direction vertical to the chord line are respectively 0.1, 0.2 and 0.3 time of the chord length of the main wing, one end of each row wing is respectively and fixedly arranged on an airplane body, the other end of each row wing is respectively and fixedly arranged on a connecting plate, and the connecting plate is fixedly arranged on the lower surface of the wing. When the flow guide blade grid is used under the wing, the airflow is guided by the blade grid, a certain retardant effect is formed on the airflow, a large-range high-pressure region is formed at the lower surface of the wing, and in addition, because the lift force effect is also realized on the three groups of row wings, the lift force of the wing is effectively improved.
Description
Technical field
The present invention relates to the aerodynamic arrangement field of aircraft, specifically a kind of high lift device that can realize aircraft short take-off and landing (STOL).
Background technology
Because unmanned plane has the advantages such as cost is low, no one was injured, viability is strong, easy to use, unmanned plane is more and more widely used in battle reconnaissance and supervision, electronic warfare, positioning school and the civil areas such as military field and border patrols, Aerial photography, traffic monitoring, the condition of a disaster supervision such as penetrates.Owing to being subject to field domain condition restriction, the unmanned plane with short take-off and landing (STOL) ability often more can complete aerial mission efficiently.
Short take-off and landing (STOL) technology mainly contains at present: 1. adopt advanced aerodynamic arrangement, change wing profile and aspect; 2. adopt complicated mechanical high lift device; 3. engine installation verts; 4. adopt the power-boosting device as jet flap etc.Wherein mechanical high lift device needs complexity and accurate wing flap jack, and additional mechanism design cost and structural weight are all very large; Engine installation and the jet flap technical pattern of verting is more complicated, and cost is also very high, and the stability and control of aircraft is had higher requirement, and is obviously not suitable for being used on blimp.Therefore, seeking new technology on pneumatic is more suitable for as blimps such as unmanned planes.
Summary of the invention
In order to overcome, the complex structure weight existing in prior art is large, cost is high, is unsuitable for the deficiency of blimp, and the present invention proposes a kind of guide-ring of aircraft short take-off and landing (STOL).
The row's of the present invention includes wing and row's wing connecting panel.Row's wing by upper row's wing, in row's wing and lower row's wing form.The chord length of upper row's wing, middle row's wing and lower row's wing is 10% of wing chord length, and length is 80% of wing length.Each arranges the wing all around the line of centers deflection of self length direction, and its deflection angle is: the deflection angle of above arranging the wing 3 is 11 °, and the deflection angle of middle row's wing is 13 °, and the deflection angle of lower row's wing 5 is 15 °.
In chordwise direction, the distance of the axis of upper row's wing and host wing leading edge is 1.05 times of main wing chord lengths, and the distance of the axis of middle row's wing and host wing leading edge is 1.15 times of main wing chord lengths, and the distance of the axis of lower row's wing and host wing leading edge is 1.25 times of main wing chord lengths.
Arrange the axis of the wing on perpendicular to string of a musical instrument direction and the distance of host wing leading edge is 0.1 times of main wing chord length, the distance of the axis of middle row's wing and host wing leading edge is 0.2 times of main wing chord length, and the distance of the axis of lower row's wing and host wing leading edge is 0.3 times of main wing chord length.
One end of described upper row's wing, middle row's wing and lower row's wing is all fixed on fuselage, and the other end is all on the row's of being fixed on wing connecting panel.Row's wing connecting panel is vertically fixed on the lower surface of wing.Upper row's wing, middle row's wing and lower row's wing are NACA2310 straight wing.
When the present invention is used for wing below, make air-flow be subject to guiding and the inhibitory action of leaf grating simultaneously, thereby changed wing flow field around.Air-flow, owing to being subject to the inhibitory action of leaf grating, makes the lower surface of wing form large-scale higher-pressure region, and the effect of the high pressure draft of wing lower surface to wing improved the lift of wing; And three groups of row's wings, in the used time of doing that is subject to air-flow, also can produce lift, thereby the lift efficiency of wing have had significant raising.
If Fig. 6 is the lift efficiency contrast of installing guide-ring front and back aircraft additional.Numerical modelling is carried out in flow field when flying speed is 8m/s.Analog result demonstration, under the same elevation angle, the lift efficiency of aircraft is significantly improved.By apply guide-ring below aircraft wing trailing edge, improve the lift efficiency of wing, realized the short take-off and landing (STOL) of aircraft, reduced the restriction of landing environment to aircraft; And guide-ring lift-rising of the present invention device simple structure used, lift-rising is reliable for effect, is convenient to demolition and maintenance.
Accompanying drawing explanation
Fig. 1 is the aircraft guide-ring layout under half module;
Fig. 2 is guide-ring front elevation;
Fig. 3 is guide-ring partial enlarged drawing;
Fig. 4 is wing and guide-ring section-drawing;
Fig. 5 installs guide-ring front and back airplane ascensional force Character Comparison additional.Wherein:
1. on fuselage 2. host wings 3., arrange and in the wing 4., arrange 5. times row's wings of the wing, 6. row's wing connecting panels
The specific embodiment
The present embodiment is a kind of aircraft short take-off and landing (STOL) guide-ring, comprises row's wing and row's wing connecting panel 6.Described row's wing comprises row's wing 3, middle row's wing 4 and lower row's wing 5.
The airplane main wing 2 of the present embodiment is traditional straight wing, adopts NACA2413 aerofoil profile, wing aspect ratio 8.85, and fuselage stagger angle is 5 ° relatively.As shown in Fig. 1 Fig. 2, guide-ring adopts row's wing layout, and upper row's wing 3, middle row's wing 4 and lower row's wing 5 are NACA2310 straight wing.The chord length of upper row's wing 3, middle row's wing 4 and lower row's wing is 10% of wing chord length, and length is 80% of wing length.As shown in Figure 3, each is arranged the wing all to take the line of centers of self length direction is axis; Each arranges the wing around described self axis tilt, and its deflection angle is: the deflection angle of above arranging the wing 3 is 11 °, and the deflection angle of middle row's wing 4 is 13 °, and the deflection angle of lower row's wing 5 is 15 °.
In chordwise direction, the distance of the axis of upper row's wing 3 and host wing leading edge is 1.05 times of main wing chord lengths, and the distance of the axis of middle row's wing 4 and host wing leading edge is 1.15 times of main wing chord lengths, and the distance of the axis of lower row's wing 5 and host wing leading edge is 1.25 times of main wing chord lengths.
Arrange the axis of the wing 3 on perpendicular to string of a musical instrument direction and the distance of host wing leading edge is 0.1 times of main wing chord length, the distance of the axis of middle row's wing 4 and host wing leading edge is 0.2 times of main wing chord length, and the distance of the axis of lower row's wing 5 and host wing leading edge is 0.3 times of main wing chord length.
One end of described upper row's wing 3, middle row's wing 4 and lower row's wing 5 is all fixed on fuselage, and the other end is all fixed on connecting panel 6.Plate connects 6 to be made by carbon fibre material, is vertically fixed on the lower surface of wing 2.
When the present embodiment is used for wing below, make air-flow through the guiding of leaf grating and air-flow is formed to certain inhibitory action, lower surface at wing has formed large-scale higher-pressure region, and owing to also thering is lift effect on three groups of row's wings, thereby effectively improved the lift of wing.
If Fig. 6 is the lift efficiency contrast of installing guide-ring front and back aircraft additional.When flying speed is 8m/s, stream field carries out numerical modelling.Analog result demonstration, the lift efficiency of aircraft has had significant raising.
Claims (3)
1. a guide-ring for aircraft short take-off and landing (STOL), is characterized in that, comprises row's wing and row's wing connecting panel; Row's wing by upper row's wing, in row's wing and lower row's wing form; The chord length of upper row's wing, middle row's wing and lower row's wing is 10% of wing chord length, and length is 80% of wing length; Each arranges the wing all around the line of centers deflection of self length direction, and its deflection angle is: the deflection angle of above arranging the wing is 11 °, and the deflection angle of middle row's wing is 13 °, and the deflection angle of lower row's wing 5 is 15 °; In chordwise direction, the distance of the axis of upper row's wing and host wing leading edge is 1.05 times of main wing chord lengths, and the distance of the axis of middle row's wing and host wing leading edge is 1.15 times of main wing chord lengths, and the distance of the axis of lower row's wing and host wing leading edge is 1.25 times of main wing chord lengths;
Arrange the axis of the wing on perpendicular to string of a musical instrument direction and the distance of host wing leading edge is 0.1 times of main wing chord length, the distance of the axis of middle row's wing and host wing leading edge is 0.2 times of main wing chord length, and the distance of the axis of lower row's wing and host wing leading edge is 0.3 times of main wing chord length;
One end of described upper row's wing, middle row's wing and lower row's wing is all fixed on fuselage, and the other end is all on the row's of being fixed on wing connecting panel.
2. a kind of guide-ring of aircraft short take-off and landing (STOL) as claimed in claim 1, is characterized in that, row's wing connecting panel is vertically fixed on the lower surface of wing.
3. a kind of guide-ring of aircraft short take-off and landing (STOL) as claimed in claim 1, is characterized in that, described upper row's wing, middle row's wing and lower row's wing are NACA2310 straight wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110284902.9A CN102390522B (en) | 2011-09-22 | 2011-09-22 | Flow guide blade grid for short-distance takeoff and landing of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110284902.9A CN102390522B (en) | 2011-09-22 | 2011-09-22 | Flow guide blade grid for short-distance takeoff and landing of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102390522A CN102390522A (en) | 2012-03-28 |
| CN102390522B true CN102390522B (en) | 2014-03-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110284902.9A Expired - Fee Related CN102390522B (en) | 2011-09-22 | 2011-09-22 | Flow guide blade grid for short-distance takeoff and landing of airplane |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803060A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Unmanned plane single-spoiler empennage |
| CN103612745A (en) * | 2013-10-25 | 2014-03-05 | 苏州艾锐泰克无人飞行器科技有限公司 | Unmanned aerial vehicle boost spoiler |
| CN103786872A (en) * | 2013-10-25 | 2014-05-14 | 苏州艾锐泰克无人飞行器科技有限公司 | Low-speed balance wing of unmanned aerial vehicle |
| CN103803062A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Interceptor arranged at bottom of tail of unmanned aerial vehicle (UAV) |
| CN103786873A (en) * | 2013-10-25 | 2014-05-14 | 苏州艾锐泰克无人飞行器科技有限公司 | Interceptor for airframe bottom of unmanned plane |
| CN103803061A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Multi-interceptor empennage of unmanned aerial vehicle (UAV) |
| CN103803058A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Single-interceptor side wing of unmanned aerial vehicle (UAV) |
| CN104192296B (en) * | 2014-09-01 | 2016-02-17 | 西北工业大学 | The straight wing high lift device of parallel-moving type of variable high spud angle |
| CN105947176B (en) * | 2016-04-08 | 2018-10-30 | 梁平 | Composite wing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1787321A (en) * | 1929-08-12 | 1930-12-30 | Orr Matthew | Airplane wing |
| US1879338A (en) * | 1928-06-17 | 1932-09-27 | Handley Page Ltd | Aeroplane wing with guide blades |
| US3807663A (en) * | 1972-09-15 | 1974-04-30 | Ball Brothers Res Corp | Air foil structure |
| CH694987A5 (en) * | 2004-01-07 | 2005-10-31 | Ulrich La Roche | Aircraft wing with grid joined to exterior of main part has grid parts fixed to main part by individual, curved transition pieces |
| CN202279230U (en) * | 2011-09-22 | 2012-06-20 | 西北工业大学 | Flow guiding grid plate for lift augmentation of airplane |
-
2011
- 2011-09-22 CN CN201110284902.9A patent/CN102390522B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1879338A (en) * | 1928-06-17 | 1932-09-27 | Handley Page Ltd | Aeroplane wing with guide blades |
| US1787321A (en) * | 1929-08-12 | 1930-12-30 | Orr Matthew | Airplane wing |
| US3807663A (en) * | 1972-09-15 | 1974-04-30 | Ball Brothers Res Corp | Air foil structure |
| CH694987A5 (en) * | 2004-01-07 | 2005-10-31 | Ulrich La Roche | Aircraft wing with grid joined to exterior of main part has grid parts fixed to main part by individual, curved transition pieces |
| CN202279230U (en) * | 2011-09-22 | 2012-06-20 | 西北工业大学 | Flow guiding grid plate for lift augmentation of airplane |
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| CN102390522A (en) | 2012-03-28 |
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